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The International Standard Atmosphere (ISA) is an United States Government, publish extensions or subsets of the same atmospheric model under their own standards-making authority.
The ISA mathematical model divides the atmosphere into layers with linear temperature distributions against geopotential altitude.^{[2]} The other two values (pressure and density) are computed by simultaneously solving the equations resulting from:
Air density must be calculated in order to solve for the pressure, and is used in calculating dynamic pressure for moving vehicles. Dynamic viscosity is an empirical function of temperature, and kinematic viscosity is calculated by dividing dynamic viscosity by the density.
Thus the standard consists of a tabulation of values at various altitudes, plus some formulas by which those values were derived. For example, at mean sea level the standard gives a pressure of 101,325 pascals (14.6959 psi) (1 atm), a temperature of 15 °C (59 °F), a temperature lapse rate of −6.5 °C (20.3 °F) per km (roughly −2°C (-3.6°F) per 1,000 ft), and a density of 1.2250 kilograms per cubic meter (0.07647 lb/cu ft). The tropospheric tabulation continues to 11,000 meters (36,089 ft), where the pressure has fallen to 22,632 pascals (3.2825 psi), the temperature to −56.5 °C (−69.7 °F), and the density to 0.3639 kilograms per cubic meter (0.02272 lb/cu ft). Between 11 km and 20 km, the temperature remains constant.^{[3]}^{[4]}
To allow modeling conditions below mean sea level, the troposphere actually extends to about −610 meters (−2,000 ft), where the temperature is 19 °C (66 °F), pressure is 108,900 pascals (15.79 psi), and density is 1.2985 kilograms per cubic meter (0.08106 lb/cu ft).
In the above table, geopotential altitude is calculated from a mathematical model that adjusts the altitude to include the variation of gravity with height, while geometric altitude is the standard direct vertical distance above mean sea level.^{[2]} Note that the Lapse Rates cited in the table are given as °C per kilometer of geopotential altitude, not geometric altitude.
The ISA model is based on average conditions at mid latitudes, as determined by the ISO's TC 20/SC 6 technical committee. It has been revised from time to time since the middle of the 20th century.
The ISA is considered to model a standard day to allow a reproducible engineering reference for calculation and testing of engine and vehicle performance at various altitudes. It does not provide a rigorous meterological model of actual atmospheric conditions (for example, changes in barometric pressure due to wind conditions). Non-standard (hot or cold) days are modeled by adding a specified temperature delta to the standard temperature at altitude, but pressure, density, and viscosity are not recalculated at the resultant non-standard temperature. (Thus the temperature effects on them are considered to be much less important than the effect of altitude.) Hot day, Cold day, Tropical, and Polar temperature profiles with altitude, such as United States Department of Defense MIL-STD-210A, have been defined for use as performance references.
The International Civil Aviation Organization (ICAO) published their "ICAO Standard Atmosphere" as Doc 7488-CD in 1993. It has the same model as the ISA, but extends the altitude coverage to 80 kilometers (262,500 feet).^{[6]}
The ICAO Standard Atmosphere does not contain water vapour.
Some of the values defined by ICAO are:
Aviation standards and flying rules are based on the International Standard Atmosphere. Airspeed indicators are calibrated on the assumption that they are operating at sea level in the International Standard Atmosphere where the air density is 1.225 kg/m^{3}. The standard is very useful in meteorology for comparison against actual values.
The
http://www.pdas.com/refs/us76.pdf
The standard conditions for temperature and pressure are a model of gas temperature and pressure used in chemistry.
NRLMSISE-00 is a newer model of the Earth's atmosphere from ground to space, developed by the US Naval Research Laboratory taking actual satellite drag data into account. A primary use of this model is to aid predictions of satellite orbital decay due to atmospheric drag.
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